CN115165297A - Mortise-tenon joint structure piece type hinge moment balance - Google Patents
Mortise-tenon joint structure piece type hinge moment balance Download PDFInfo
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- CN115165297A CN115165297A CN202211086975.1A CN202211086975A CN115165297A CN 115165297 A CN115165297 A CN 115165297A CN 202211086975 A CN202211086975 A CN 202211086975A CN 115165297 A CN115165297 A CN 115165297A
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- balance
- wing
- mortise
- hinge moment
- tenon joint
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a mortise-tenon joint structure sheet type hinge moment balance, belongs to the field of aerospace aerodynamic force test measuring equipment, and aims to solve the problem that the measuring accuracy of the balance is influenced by pre-tightening stress of the sheet type hinge moment balance and wings which are connected through threads. The device comprises a measuring rudder, a balance element and a balance connecting part; the balance connecting part is a T-shaped straight beam, two ends of the balance element are respectively connected with the balance connecting part and the measuring rudder, a square notch is arranged at one end, close to the wing tip, of the rear edge of the wing, a T-shaped groove is formed in the end face, close to one side of the front edge of the wing, of the square notch, the balance connecting part is in mortise-tenon connection with the T-shaped groove, and two ends of the balance connecting part are respectively abutted against the wing tip and the wing tip. The area of the connecting surface of the hinge moment balance of the mortise and tenon joint structure is far smaller than that of the torque balance connecting surface of the threaded connection, and the influence of the pretightening force of the threaded connection is avoided, so that the connection stress can be effectively reduced or eliminated, and the measurement accuracy of the sheet type hinge moment balance can be effectively improved.
Description
Technical Field
The invention belongs to the field of aerospace aerodynamic force test measuring equipment, and particularly relates to a mortise-tenon joint structure sheet type hinge moment balance.
Background
Wind tunnel balances are used in wind tunnel tests to measure aerodynamic loads acting on aircraft models. According to the working principle, the device can be divided into a mechanical balance, a strain balance, a piezoelectric balance, a magnetic suspension balance and the like. At present, a strain balance is commonly used, a strain electric measurement principle is adopted, a balance element is designed by orthogonally decomposing a pneumatic load, and a strain gauge for sensing deformation is adhered to the balance element to form an electric bridge, so that the measurement of the pneumatic load is realized.
The sheet type hinge moment balance is one of strain balances and is mainly used for measuring the hinge moment aerodynamic load of an aircraft model control surface.
Disclosure of Invention
The invention aims to provide a sheet type hinge moment balance with a mortise-tenon joint structure, which aims to solve the problem that the measurement accuracy of the balance is influenced because the connecting part of the sheet type hinge moment balance is in threaded connection with the wings of an aircraft model, and the stress of the threaded connection is transmitted to balance elements. The technical scheme adopted by the invention is as follows:
a mortise and tenon joint structure sheet type hinge moment balance comprises a measuring rudder, a balance element and a balance connecting part; the balance element comprises a plurality of beam-shaped components arranged at intervals, the balance connecting part is a T-shaped straight beam, one end of the balance element is connected with the middle protruding end of the balance connecting part, the other end of the balance element is connected with one side of the measuring rudder, the wing and the wing of the aircraft model are slightly abutted and connected, one end of the rear edge of the wing, which is close to the wing, is provided with a square notch for the moment balance to be installed, the square notch is close to a T-shaped groove formed in the end face of one side of the front edge of the wing, the balance connecting part is in mortise and tenon connection with the T-shaped groove, and the two ends of the balance connecting part are slightly abutted against the wing and the wing respectively.
Furthermore, the control surface of the measuring rudder is matched with the trailing edge of the wing.
Further, the number of the beam-shaped members is three.
Further, the beam-like member is a rectangular straight beam.
Furthermore, the measuring rudder, the balance element and the balance connecting part are of an integral structure.
Compared with the prior art, the invention has the beneficial effects that:
the hinge moment balance with the mortise-tenon connection structure is characterized in that the connection surface of the hinge moment balance is the end surface of the balance connection part close to one side of the front edge of the wing, the area of the connection surface is far smaller than that of the moment balance in threaded connection, the influence of the pretightening force of the threaded connection is avoided, the connection stress can be effectively reduced or eliminated, and the measurement accuracy of the sheet type hinge moment balance can be effectively improved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the assembly of the present invention with a wing and wing tip;
FIG. 3 is a partial schematic view of an airfoil.
In the figure: 1-measuring rudder, 2-balance element, 3-balance connecting part, 4-wing, 41-square notch, 42-T-shaped groove and 5-wing tip.
Detailed Description
In order that the objects, aspects and advantages of the invention will become more apparent, the invention will be described by way of example only, and in connection with the accompanying drawings. It is to be understood that this description is made only by way of example and not as a limitation on the scope of the invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The connection mentioned in the invention is divided into fixed connection and detachable connection, the fixed connection is non-detachable connection and comprises but is not limited to folding edge connection, rivet connection, bonding connection, welding connection and other conventional fixed connection modes, the detachable connection comprises but is not limited to bolt connection, buckle connection, pin connection, hinge connection and other conventional detaching modes, when the specific connection mode is not clearly limited, the skilled person can select at least one connection mode from the existing connection modes to realize the function by default, and the skilled person can select the connection mode according to the needs. For example: the fixed connection selects welding connection, and the detachable connection selects bolt connection.
The present invention will be described in further detail with reference to the accompanying drawings, and the following examples are illustrative of the present invention, but the present invention is not limited to the following examples.
Example (b): as shown in fig. 1-3, a mortise and tenon joint structure sheet type hinge moment balance comprises a measuring rudder 1, a balance element 2 and a balance connecting part 3; balance component 2 comprises a plurality of interval arrangements's beam-shaped component, and balance connecting portion 3 is the straight roof beam of T shape, and the one end of balance component 2 links to each other with the middle protruding end of balance connecting portion 3, and the other end of balance component 2 links to each other with one side of measuring rudder 1, and aircraft model's wing 4 supports with wing slightly 5 and leans on continuously, and the trailing edge of wing 4 is close to the one end that wing slightly 5 was equipped with square notch 41 that can supply the moment balance installation, square notch 41 is close to be equipped with T-slot 42 on the leading edge side end face of wing 4, balance connecting portion 3 and T-slot 42 mortise-tenon joint, and balance connecting portion 3's both ends are leaned on with wing 4 and wing slightly 5 respectively, and wing slightly 5 is used for complementing airfoil.
The control surface of the measuring rudder 1 is matched with the trailing edge of the wing 4.
The number of the beam-shaped members is three.
The beam-like member is a rectangular straight beam.
The measuring rudder 1, the balance element 2 and the balance connecting part 3 are of an integral structure.
When the hinge moment balance is used, a strain gauge which senses deformation is stuck on the balance element 2 to form an electric bridge, so that the measurement of pneumatic load is realized.
The hinge moment balance with the mortise and tenon connection structure has the advantages that the connection surface of the hinge moment balance is the front edge side end surface of the balance connection part 3 close to the wing 4, the area of the connection surface is far smaller than that of the moment balance in threaded connection, the influence of the pretightening force of the threaded connection is avoided, the connection stress can be effectively reduced or eliminated, and the measurement accuracy of the sheet type hinge moment balance can be effectively improved.
The above embodiments are merely illustrative of the present patent and do not limit the scope of the patent, and those skilled in the art can make modifications to the parts thereof without departing from the spirit and scope of the patent.
Claims (5)
1. The utility model provides a mortise-tenon joint structure piece formula hinge moment balance which characterized in that: comprises a measuring rudder (1), a balance element (2) and a balance connecting part (3); balance component (2) comprise a plurality of interval arrangements's beam-shaped component, and balance connecting portion (3) are the straight roof beam of T shape, and the one end of balance component (2) links to each other with the middle protruding end of balance connecting portion (3), and the other end of balance component (2) links to each other with a side of measuring rudder (1), and wing (4) and the wing of aircraft model lean on slightly (5) and link to each other, and the one end that the trailing edge of wing (4) is close to wing slightly (5) is equipped with square notch (41) that can supply moment balance installation, square notch (41) are close to be equipped with T-slot (42) on the leading edge side end face of wing (4), balance connecting portion (3) and T-slot (42) mortise-tenon joint, the both ends of balance connecting portion (3) lean on with wing (4) and wing slightly (5) respectively.
2. The mortise-tenon joint structure sheet type hinge moment balance according to claim 1, characterized in that: the control surface of the measuring rudder (1) is matched with the rear edge of the wing (4).
3. The mortise-tenon joint structure sheet type hinge moment balance according to claim 1, characterized in that: the number of the beam-shaped members is three.
4. The mortise-tenon joint structure sheet type hinge moment balance according to claim 1, characterized in that: the beam-like member is a rectangular straight beam.
5. The mortise-tenon joint structure sheet type hinge torque balance according to any one of claims 1 to 4, wherein: the measuring rudder (1), the balance element (2) and the balance connecting part (3) are of an integral structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086975.1A CN115165297B (en) | 2022-09-07 | 2022-09-07 | Mortise-tenon joint structure sheet type hinge moment balance |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086975.1A CN115165297B (en) | 2022-09-07 | 2022-09-07 | Mortise-tenon joint structure sheet type hinge moment balance |
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| CN115165297A true CN115165297A (en) | 2022-10-11 |
| CN115165297B CN115165297B (en) | 2022-11-08 |
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| CN202211086975.1A Active CN115165297B (en) | 2022-09-07 | 2022-09-07 | Mortise-tenon joint structure sheet type hinge moment balance |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10132698A (en) * | 1996-10-31 | 1998-05-22 | Mitsubishi Heavy Ind Ltd | Angle changing device for wind-tunnel model |
| CN105115694A (en) * | 2015-07-21 | 2015-12-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Piece type hinge moment balance |
| CN111175014A (en) * | 2020-02-28 | 2020-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Balance system and method for accurately measuring rotor wing pneumatic load |
| CN111947879A (en) * | 2020-08-31 | 2020-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet flow test device for wind tunnel model |
| CN112693623A (en) * | 2020-12-21 | 2021-04-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Missile grid rudder hinge moment model claw disc type self-locking positioning structure |
| CN113267317A (en) * | 2021-05-10 | 2021-08-17 | 中国航空工业集团公司哈尔滨空气动力研究所 | Hinge moment balance interference elimination structure |
-
2022
- 2022-09-07 CN CN202211086975.1A patent/CN115165297B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10132698A (en) * | 1996-10-31 | 1998-05-22 | Mitsubishi Heavy Ind Ltd | Angle changing device for wind-tunnel model |
| CN105115694A (en) * | 2015-07-21 | 2015-12-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Piece type hinge moment balance |
| CN111175014A (en) * | 2020-02-28 | 2020-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Balance system and method for accurately measuring rotor wing pneumatic load |
| CN111947879A (en) * | 2020-08-31 | 2020-11-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet flow test device for wind tunnel model |
| CN112693623A (en) * | 2020-12-21 | 2021-04-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Missile grid rudder hinge moment model claw disc type self-locking positioning structure |
| CN113267317A (en) * | 2021-05-10 | 2021-08-17 | 中国航空工业集团公司哈尔滨空气动力研究所 | Hinge moment balance interference elimination structure |
Non-Patent Citations (5)
| Title |
|---|
| GOMATHINAYAGAMBALAKALYANI，GOPALANJAGADEESH: "《An accelerometer balance for aerodynamic force measurements over Hypervelocity Ballistic models in shock tunnel》", 《MEASUREMENT》 * |
| 向立光，舒海峰等: "《通气模型高超声速风洞铰链力矩试验技术研究》", 《飞行力学》 * |
| 李勇，吴天正: "《铰链力矩天平结构参数对升力测量的影响规律》", 《弹箭与制导学报》 * |
| 李勇，赵长辉等: "《多支撑天平测量技术研究与应用》", 《弹箭与制导学报》 * |
| 李勇，赵长辉等: "《翼型测力天平的研制》", 《实验流体力学》 * |
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| CN115165297B (en) | 2022-11-08 |
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